(b)  
The aft static ports (S2) in the lower left pitot-static probe.

 S 845-184
 (11)
 Examine the static ports for unwanted materials and rough locations on the inner and outer surfaces (Ref 34-11-01/601).

 S 845-185

 (12)
 Remove the DO-NOT-CLOSE tags and close these circuit breakers:

 (a)  P6 Main Power Distribution Panel
 1) 6D31 PROBE HEAT PITOT R

 EFFECTIVITYùùùùùùùùùùùùùùùùùùùùùùùùùùùùùù. ú

 34-11-00
 ALL  ú ú 02 Page 532 ú Feb 18/01
BOEING PROPRIETARY - Copyright (C) - Unpublished Work - See title page for details.
A
747-400 MAINTENANCE MANUAL
 2) 6D32 PROBE HEAT AUX PITOT L 3) 6E01 PRIM T/E FLAP CONT AC 4) 6E02 PRIM T/E FLAP CONT DC
 TASK 34-11-00-795-186
 9.  The Auxiliary No. 1 Static System Leak Test (Full-Range)________________________________________________________
 A. Standard Tools and Equipment
 (1)  
Pneumatic Test Set

 (a) Vacuum source, 10 to 30 inches of mercury (absolute)

 (2)  
Gages

 (a)  Static system test gage - required to indicate 10 to 30 inches of mercury (absolute) with accuracy of |0.1 (readable to |0.01) inch of mercury or |200 (readable to |20) feet.

 (3)  
Flow restrictors, control valves, cutoff valves, and pressure tape as required.

 B. References
 (1)  34-11-01/601, Pitot-Static Probe
 C. Access
 (1)  Location Zone 115 Area Between Nose Gear Well and Fuselage, LH 116 Area Between Nose Gear Well and Fuselage, RH 117 Electrical and Electronics Compartment, LH
 D. Procedure
 S 865-275
 WARNING: MAKE SURE THAT YOU DO NOT APPLY ELECTRICAL POWER TO THE FLIGHT
_______ CONTROLS. FLIGHT CONTROL SURFACES CAN MOVE AUTOMATICALLY WHEN YOU PRESSURIZE THE PITOT-STATIC SYSTEM. THIS CAN CAUSE INJURIES TO PERSONS AND DAMAGE TO EQUIPMENT.
 CAUTION: MAKE SURE THAT YOU DO NOT APPLY ELECTRICAL POWER TO THE
_______ PITOT-STATIC PROBE HEATERS. YOU CAN CAUSE DAMAGE TO THE PITOT-STATIC PROBES.
 (1)  Open these circuit breakers and attach DO-NOT-CLOSE tags:
 (a)  P6 Main Power Distribution Panel
 1) 6D30 PROBE HEAT PITOT L
 2) 6D33 PROBE HEAT AUX PITOT R
 3) 6E01 PRIM T/E FLAP CONT AC
 4) 6E02 PRIM T/E FLAP CONT DC

 EFFECTIVITYùùùùùùùùùùùùùùùùùùùùùùùùùùùùùù. ú

 34-11-00
 ALL  ú ú 02 Page 533 ú Feb 18/01
BOEING PROPRIETARY - Copyright (C) - Unpublished Work - See title page for details.
A
747-400 MAINTENANCE MANUAL
 S 485-279
 WARNING:_______MAKE SURE THAT THE PROBE HEAT IS NOT ON. YOU CAN CAUSE INJURY TO PERSONS.
 WARNING: WHEN THE STATIC PORTS ARE COVERED, MAKE SURE THAT CONDITION IS
_______ VISIBLE FROM THE GROUND. FAILURE TO OBSERVE AND REMOVE COVERINGS OVER STATIC PORTS BEFORE FLIGHT MAY CAUSE LARGE ERRORS ON AIRSPEED SENSING AND ALTITUDE SENSING SIGNALS, WHICH MAY LEAD TO LOSS OF SAFE FLIGHT.
 CAUTION:_______DO NOT EXTEND THE SEALS INTO THE PITOT DRAINS. YOU CAN CAUSE DAMAGE TO THE SURFACE IN THE AREA WHEN YOU REMOVE THE SEALS.
 (2)  Seal these locations with vinyl adhesive tape:
 (a)  
The forward static ports (S1) in the lower right pitot-static probe.

 (b)  
The aft static ports (S2) in the upper left pitot-static probe.

 S 865-189
 CAUTION:_______DISCONNECT THE SOURCE SELECT VALVE FROM THE STATIC SYSTEM. YOU CAN CAUSE DAMAGE TO THE AIR DATA COMPUTER.
 (3)  
Disconnect the auxiliary No. 1 static system from the input of the source select valve.

 S 865-190

 (4)  
Connect the pneumatic test set to the auxiliary No. 1 static system test fitting.

 (a)  
Connect the static (vacuum) source in the pneumatic test unit through the static control valve to the static cutoff valve.

 (b)  
Connect the quick-disconnect test fitting of the auxiliary No. 1 static system to the static cutoff valve through the static system test gage and flow restrictor.

 NOTE: You will find the test fitting on the left side of the
　
中國航空網 www.k6050.com
航空翻譯 www.aviation.cn
本文鏈接地址：747-400 AMM 飛機維護手冊 導航 NAVIGATION 1(49)